Windshield wiper fluid dispensing system

ABSTRACT

An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application is a divisional of U.S. application Ser. No. 17/410,217filed Aug. 24, 2021 for “WINDSHIELD WIPER FLUID DISPENSING SYSTEM,”which in turn claims the benefit of Indian Provisional Application No.202141013512 filed Mar. 26, 2021 for “WINDSHIELD WIPER FLUID DISPENSINGSYSTEM” by B. Mugeraya and V. Balakrishnan, the disclosures of which areincorporated in their entireties by reference.

BACKGROUND

The present disclosure relates to windshield wiper systems, and inparticular to a windshield wiper system used on an aircraft.

Aircraft windshield wiper systems are used to wipe and clean water orother debris from an aircraft windshield, allowing better visibility outthe windshield for both the pilot and co-pilot. Windshield wiper systemsinclude a wiper arm and a wiper blade that sweep back and forth across awindshield, cleaning the windshield for the pilot and co-pilot.Traditionally, windshield wiper systems include fluid nozzles extendingthrough the body of the aircraft and positioned adjacent an edge of thewindshield on the aircraft. The fluid nozzles spray a cleaning fluidfrom the edge of the windshield, reaching only a limited portion of thewindshield. As such, current windshield wiper systems includingtraditional fluid nozzles are limited in their ability to clean water orother debris from the aircraft windshield.

SUMMARY

According to one aspect of the disclosure, a windshield wiper system foruse on a windshield of an aircraft is disclosed. The windshield wipersystem includes a wiper, a nozzle, an actuator, a controller, a userinterface, a fluid control unit, and a fluid source. The wiper includesa wiper arm and a wiper blade coupled to a first end of the wiper arm.The nozzle is coupled to the wiper blade and the nozzle is configured todispense a fluid. The actuator includes an output shaft coupled to asecond end of the wiper arm. The controller is electrically coupled toeach of the actuator, user interface, and fluid control unit. The fluidsource is fluidly coupled to the nozzle through a fluid line.

According to another aspect of the disclosure, a method of operating awindshield wiper system for use on a windshield of an aircraft isdisclosed. The method including the steps of: transferring, by acontroller, a command signal to an electrically coupled fluid controlunit to activate the fluid control unit; transferring, by the fluidcontrol unit, a fluid from a fluid source through a fluid line to anozzle coupled to a wiper blade; and dispensing, by the nozzle, thefluid onto the windshield of the aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A is a side view of a windshield wiper system on an aircraftwindshield.

FIG. 1B is a schematic block diagram of the windshield wiper system.

FIG. 2A is a perspective view of a first embodiment of a wiper bladeincluding integrated nozzles.

FIG. 2B is a perspective view of a second embodiment of a wiper bladeincluding integrated nozzles.

DETAILED DESCRIPTION

FIG. 1A is a side view of windshield wiper system 10 on windshield 12 ofan aircraft (not shown). FIG. 1B is a schematic block diagram ofwindshield wiper system 10. FIGS. 1A-1B will be discussed together.Further, hereinafter windshield wiper system 10 will be referred to asWWS 10. WWS 10 includes wiper 14, output shaft 16, actuator 18, gearreduction 20, controller 22, fluid control unit 24, fluid source 26,fluid line 28, nozzle 30, and user interface 32. WWS 10 is installed onan aircraft and WWS 10 is configured to clear windshield 12 of rain orother debris.

Wiper 14 includes wiper arm 34 and wiper blade 36. Wiper arm 34 includesfirst end 34A positioned at a distal end of wiper arm 34 and second end34B positioned at an opposite distal end of wiper 14 as first end 34A.Wiper blade 36 is coupled to first end 34A of wiper arm 34 through amechanical connection, such as a threaded or clamping connection. Wiperarm 34 can be constructed from a polymer, a composite, or a metal, amongother options. Wiper arm 34 is coupled to output shaft 16 at second end34B of wiper arm 34 through a mechanical connection, such as a threadedor clamping connection. Output shaft 16 extends through a body portionof the aircraft adjacent windshield 12 but not through windshield 12.Output shaft 16 is configured to rotate about its central axis,providing rotational energy to second end 34B of wiper arm 34, which inturn forces wiper 14 to traverse across windshield 12 in a sweepingmotion.

Actuator 18 is coupled to output shaft 16 within the body portion of theaircraft. Actuator 18 is configured to provide rotational energy tooutput shaft 16, rotating output shaft 16 about its central axis. Therotation of output shaft 16 forces wiper 14 to traverse acrosswindshield 12 in a sweeping motion, therefore actuator 18 provides theenergy necessary to drive motion of wiper 14. In the embodiment shown,actuator 18 is a brushless direct current motor. In another embodiment,actuator 18 can be a brushed direct current motor or any other motorconfigured to provide rotational energy to output shaft 16. Further,actuator 18 is a bi-directional motor that can operate in bothdirections, allowing output shaft 16, wiper arm 34, and wiper blade 36to travel across windshield 12 in both directions. Actuator 18 iscoupled to output shaft 16 through gear reduction 20, in which gearreduction 20 is positioned between output shaft 16 and actuator 18. Inother words, gear reduction 20 is positioned within the body of theaircraft, coupled at one end to output shaft 16, and coupled at theother end to actuator 18. Gear reduction 20 can include a large gearratio (greater than 3:1), such that many rotations of actuator 18 causeonly a few degrees of rotation of wiper 14. Gear reduction 20 isconfigured to provide precise angular rotation of wiper 14. In theembodiment shown in FIG. 1B, output shaft 16, actuator 18, and gearreduction 20 are shown as separate components. In another embodiment,gear reduction 20 can be integral with actuator 18 such that actuator18, gear reduction 20, and output shaft 16 are a single assembly.

In the example shown, controller 22 includes processor(s) 38, memory 40,and communication device(s) 42. However, in certain examples, controller22 can include more or fewer components than components 38, 40, and 42.Processor(s) 38, in one example, are configured to implementfunctionality and/or process instructions for execution withincontroller 22. For instance, processor(s) 38 can be capable ofprocessing instructions stored in memory 40. Examples of processor(s) 38can include any one or more of a microprocessor, a digital signalprocessor (DSP), an application specific integrated circuit (ASIC), afield-programmable gate array (FPGA), or other equivalent discrete orintegrated logic circuitry.

Memory 40 can be configured to store information within controller 22during operation of WWS 10. Memory 40, in some examples, is described ascomputer-readable storage media. In some examples, a computer-readablestorage medium can include a non-transitory medium. The term“non-transitory” can indicate that the storage medium is not embodied ina carrier wave or a propagated signal. In certain examples, anon-transitory storage medium can store data that can, over time, change(e.g., in RAM or cache). In some examples, memory 40 is a temporarymemory, meaning that a primary purpose of memory 40 is not long-termstorage. Memory 40, in some examples, is described as volatile memory,meaning that memory 40 does not maintain stored contents when power tocontroller 22 is turned off. Examples of volatile memories can includerandom access memories (RAM), dynamic random-access memories (DRAM),static random-access memories (SRAM), and other forms of volatilememories. In some examples, memory 40 is used to store programinstructions for execution by processor(s) 38. Memory 40, in oneexample, is used by software or applications running on controller 22(e.g., a software program implementing a system architecture) totemporarily store information during program execution. Memory 40, insome examples, also includes one or more computer-readable storagemedia. Memory 40 can be configured to store larger amounts ofinformation than volatile memory. Memory 40 can further be configuredfor long-term storage of information. In some examples, memory 40includes non-volatile storage elements. Examples of such non-volatilestorage elements can include magnetic hard discs, optical discs, floppydiscs, flash memories, or forms of electrically programmable memories(EPROM) or electrically erasable and programmable (EEPROM) memories.

Controller 22, in some examples, also includes communication device(s)42. Controller 22, in one example, utilizes communication device(s) 42to communicate with external devices via one or more networks, such asone or more wireless or wired networks or both. Communication device(s)42 can be a network interface card, such as an Ethernet card, an opticaltransceiver, a radio frequency transceiver, or any other type of devicethat can send and receive information. Other examples of such networkinterfaces can include Bluetooth, 3G, 4G, 5G, and Wi-Fi radio computingdevices as well as Universal Serial Bus (USB).

Controller 22 is positioned within the body portion of the aircraft andcontroller 22 is communicatively coupled to actuator 18, fluid controlunit 24, and user interface 32. Controller 22 can be communicativelycoupled to each component through electrical wires or a wirelessconnection to send and receive signals from each of actuator 18, fluidcontrol unit 24, and user interface 32. More specifically, controller 22is communicatively coupled to actuator 18 through a wired or wirelessconnection and controller 22 is configured to send command signals toactuator 18 to control operation of actuator 18. As such, controller 22can send electrical signals to and receive electrical signals fromactuator 18 to control rotation of output shaft 16 of actuator 18.Controller 22 is also communicatively coupled to fluid control unit 24through a wired or wireless connection and controller 22 is configuredto send command signals to fluid control unit 24 to control operation offluid control unit 24. As such, controller 22 can send electricalsignals to and receive electrical signals from fluid control unit 24 tocontrol dispensing of the fluid through nozzle 30. Further, controller22 is communicatively coupled to user interface 32 through a wired orwireless connection and controller 22 is configured to receive commandsignals from user interface 32 indicating an action to be performed bycontroller 22, discussed further below.

User interface 32 is positioned within the body portion of the aircraftand user interface 32 is communicatively coupled to controller 22through electrical wires or a wireless connection. User interface 32 canbe any device or component that allows the user (pilot or co-pilot) tocontrol operation of WWS 10. User interface 32 can be a graphical userinterface (GUI), a knob, a switch, a button, or any other device orcomponent that allows the user to control operation of WWS 10. In oneexample, a user can interact with user interface 32 to activate WWS 10to clear rain or debris from windshield 12 of the aircraft. Uponactivation by the user, an electrical command signal is sent from userinterface 32 to controller 22, and then controller 22 sends a commandsignal to actuator 18 and/or fluid control unit 24 to activate operationof each respective component. In another example, sensors can bepositioned on or adjacent windshield 12 and the sensors canautomatically activate WWS 10 without user interaction with userinterface 32. User interface 32 allows a pilot and/or co-pilot toactivate WWS 10, deactivate WWS 10, control the sweeping speed of wiper14 on windshield 12, control the flow rate of the fluid dispensing fromnozzle 30, control the temperature of the fluid dispensing from nozzle30, and allows the user to choose the type of fluid dispensing fromnozzle 30 onto windshield 12 of the aircraft, discussed further below.

Fluid control unit 24 is positioned within the body portion of theaircraft and fluid control unit 24 is communicatively coupled tocontroller 22 through electrical wires or a wireless connection. Fluidcontrol unit 24 includes pump 44, valve 46, bleed air valve 48, andheating element 50. Fluid control unit 24 includes computer codedinstructions that are utilized by controller 22 to activate dispensingof a fluid upon user interaction with user interface 32. Fluid controlunit 24 is communicatively coupled to controller 22, pump 44, valve 46,bleed air valve 48, and heating element 50. As discussed, controller 22can send electrical signals to and receive electrical signals from fluidcontrol unit 24 to control dispensing of the fluid. After receiving acommand signal from controller 22, fluid control unit 24 sendselectrical signals to and receives electrical signals from each of theelectrically/communicatively coupled pump 44, valve 46, bleed air valve48, and heating element 50 to control operation of each respectivecomponent.

Pump 44 is a component of fluid control unit 24 that is positionedwithin the aircraft and pump 44 is configured to force fluid toflow/travel from fluid source 26 through fluid lines 28 until the fluidreaches nozzle 30. Pump 44 can be any device that is capable of forcingthe fluid to flow/travel through fluid lines 28 as described. Pump 44can be positioned between fluid source 26 and nozzle 30 and can becoupled to fluid line 28. Fluid line 28 can be a conduit, tube, pipe,hose, or the like that includes a hollow interior portion allowingfluids to remain contained and flow within the interior of fluid lines28. Fluid lines 28 can be constructed from a metal, a polymer, or acomposite material, among other options. Fluid lines 28 are configuredto provide a flow path from fluid source 26 to nozzle 30, allowing fluidsource 26 and nozzle 30 to be fluidly coupled. In some examples, fluidsource 26 can be an impermeable vessel of any shape, size, and materialthat is configured to store the fluid that will be dispensed throughnozzle 30. In other words, fluid source 26 can be a leak proof containerthat includes a hollow interior configured to store fluids before thefluids are used by WWS 10. In other examples, fluid source 26 can be aflow path from a portion of an engine, compressor, auxiliary power unit,or any other hot air source within the aircraft, such as for example toprovide engine bleed air to nozzle 30. Fluid source 26 is positionedwithin the aircraft body, remote from nozzle 30, and fluidly coupled tonozzle 30 through fluid lines 28.

An aircraft can include a plurality of fluid sources 26, with each oneof the plurality of fluid sources 26 storing a different fluid. Forexample, one of the plurality of fluid sources 26 can be a waterreservoir configured to store water; one of the plurality of fluidsources 26 can be a windshield cleaning fluid reservoir configured tostore windshield cleaning fluid; and one of the plurality of fluidsources 26 can be a chemical rain repellant reservoir configured tostore chemical rain repellant. Additionally, one of the plurality offluid sources 26 can be a high temperature air source from a portion ofthe engine of the aircraft configured to provide bleed air to nozzle 30.An aircraft can include any number of fluid sources 26 and any desiredfluid can be stored in the fluid sources 26 to aid in cleaningwindshield 12 of the aircraft. Each of the plurality of fluid sources 26is coupled to a fluid line 28, which extends from fluid source 26 tonozzle 30. In one example, pump 44 is configured to force water to flowfrom a water reservoir (fluid source 26) through fluid line 28 and tonozzle 30. In another example, pump 44 is configured to force windshieldcleaning fluid to flow from a windshield cleaning fluid reservoir (fluidsource 26) through fluid line 28 and to nozzle 30. In another example,pump 44 is configured to force chemical rain repellant to flow from achemical rain repellant reservoir (fluid source 26) through fluid line28 and to nozzle 30. In yet another embodiment, bleed air valve 48 canbe opened to allow bleed air to flow from a high temperature air sourcewithin the engine of the aircraft through fluid line 28 and to nozzle30, discussed further below. As such, a flow path exists between each ofthe plurality of fluid sources 26 and nozzle 30, allowing each fluid tobe transferred to nozzle 30 and dispensed onto windshield 12 of theaircraft.

As discussed, fluid lines 28 can be a conduit, tube, pipe, hose, or thelike that includes a hollow interior portion allowing fluids to remaincontained and flow within the interior of fluid lines 28. Fluid lines 28can be constructed from a metal, a polymer, or a composite material,among other options. Fluid lines 28 are configured to provide a flowpath from fluid sources 26 to nozzle 30, allowing fluid sources 26 andnozzle 30 to be fluidly coupled. In the embodiment shown, fluid lines 28are coupled to each of fluid sources 26, routed through the body portionof the aircraft, routed out the body portion of the aircraft adjacentoutput shaft 16 of actuator 18, routed through a hollow interior ofwiper arm 34 to wiper blade 36, and then coupled to input port 58 ofnozzle 30. In another embodiment, fluid lines 28 can be routed fromfluid sources 26 to input port 58 following a different route or path.For example, fluid line 28 does not need to be positioned adjacentoutput shaft 16 and fluid line 28 could be coupled to an exterior ofwiper arm 34.

With that said, routing fluid lines 28 out the body portion of theaircraft adjacent output shaft 16 provides the benefit of eliminatinganother aperture extending through the body of the aircraft becausefluid line 28 can be routed through the same aperture that output shaft16 extends through. Routing fluid lines 28 through a hollow interior ofwiper arm 34 provides the benefit of increasing the aerodynamicperformance of wiper arm 34 because fluid line 28 is concealed and doesnot induce extra drag on wiper arm 34. In one embodiment, wiper arm 34can have a generally C-shaped cross-section and fluid line 28 can beattached to the hollow interior portion of wiper arm 34 throughfasteners such as clips, clamps, or screws, among other options. Inanother embodiment, wiper arm 34 can have any geometrical shapedcross-section with a hollow interior portion allowing fluid line 28 toremain concealed and coupled within the interior portion of wiper arm34. In a preferred embodiment, wiper arm 34 includes a geometrical shapethat minimizes wind resistance to increase aerodynamic efficiency of theaircraft. For example, wiper arm 34 can include smooth and/or roundededges to reduce the drag forces on wiper arm 34, improving the overallaerodynamic efficiency of wiper arm 34. Wiper arm 34 is coupled tooutput shaft 16 and wiper blade 36, facilitating the sweeping of wiperblade 36 on windshield 12. Further, wiper arm 34 includes a hollowinterior portion for containing and coupling fluid line 28, allowingfluid line 28 to be routed and coupled to input port 58 of nozzle 30while also minimizing drag forces on wiper arm 34.

Valve 46 is a component of fluid control unit 24 that is positionedwithin the aircraft and valve 46 is configured to control the flow rateof fluids travelling from fluid sources 26 to nozzle 30. Morespecifically, valve 46 is configured to control the flow rate of fluidstravelling from fluid sources 26 such as the water reservoir, windshieldcleaning fluid reservoir, and the chemical rain repellant reservoir. Inone embodiment, valve 46 can be integral with pump 44 such that valve 46and pump 44 are a single assembly. In another embodiment, valve 46 canbe a separate component from pump 44. Valve 46 is positioned betweenfluid source 26 and nozzle 30. Valve 46 is coupled to fluid line 28 tocontrol and adjust the flow rate of fluids flowing through fluid line28. Further, valve 46 is electrically coupled to fluid control unit 24,such that fluid control unit 24 controls operation of valve 46 bysending command signals to open and/or close valve 46. Likewise, bleedair valve 48 is a component of fluid control unit 24 that is positionedwithin the aircraft and bleed air valve 48 is configured to control theflow rate of high temperature bleed air travelling from the engine ofthe aircraft through fluid line 28 to nozzle 30. Bleed air valve 48 iselectrically coupled to fluid control unit 24, such that fluid controlunit 24 controls operation of bleed air valve 48 by sending commandsignals to open and/or close bleed air valve 48.

Heating element 50 is a component of fluid control unit 24 that ispositioned within the aircraft and positioned between pump 44 and nozzle30. Heating element 50 is coupled to fluid line 28 and heating element50 is configured to increase the temperature of the fluid travellingthrough fluid line 28 before the fluid reaches nozzle 30. Morespecifically, heating element 50 is configured to increase thetemperature of fluids travelling from fluid sources 26 such as the waterreservoir, windshield cleaning fluid reservoir, and the chemical rainrepellant reservoir. In one embodiment, heating element 50 is acomponent that converts electrical energy into heat through a resistanceheating element, which increases in temperature as an electric currentflows through the resistance heating element. In another embodiment,heating element 50 can be a component that receives high temperaturebleed air from the engine of the aircraft and then flows the hightemperature air around fluid line 28 to increase the temperature of thefluid flowing through fluid line 28. Heating element 50 is electricallycoupled to fluid control unit 24, such that fluid control unit 24controls operation of heating element 50 by sending command signals toincrease or decrease the temperature of heating element 50. Heatingelement 50 can increase the temperature of the fluid flowing throughfluid line 28 to aid in the cleaning of windshield 12 of the aircraft.Increasing the temperature of the fluid dispensing from nozzle 30 ontowindshield 12 can melt frozen water or other frozen debris on windshield12, providing better visibility for both the pilot and co-pilot. In theembodiment described, heating element 50 is included to increase thetemperature of fluids flowing through fluid line 28. In anotherembodiment, fluid control unit 24 can include a cooling element, such asa heat exchanger, to remove heat from the fluid flowing through fluidlines 28 to decrease the temperature of the fluid. In some examples, thecooling element can replace heating element 50 within fluid control unit24. In other examples, the cooling element can be an addition to fluidcontrol unit 24, such that fluid control unit 24 includes both heatingelement 50 and the cooling element to either heat or cool the fluid,respectively.

FIG. 2A is a perspective view of a first embodiment of wiper blade 36including nozzles 30. FIG. 2B is a perspective view of a secondembodiment of wiper blade 36 including nozzles 30. FIGS. 2A-2B will bediscussed together. Further, FIGS. 2A-2B do not show the rubber elementof wiper blade 36 that engages windshield 12, for clarity purposes. Asdiscussed, WWS 10 includes wiper 14 including wiper blade 36, fluid line28, and nozzle 30 coupled to wiper blade 36. Wiper blade 36 includeswiper support 52 configured to provide structural support to wiper blade36 and rubber element (not shown) configured to engage and cleanwindshield 12.

Nozzle 30 is coupled to wiper support 52 of wiper blade 36 and nozzle 30is configured to dispense a fluid onto windshield 12 of the aircraft.Nozzle 30 can be constructed from a polymer, a composite, or a metal,among other options. In the embodiment shown, nozzle 30 is coupled to atop surface of wiper support 52 of wiper blade 36. In anotherembodiment, nozzle 30 can be coupled to a front surface, a rear surface,or a side surface of wiper support 52 of wiper blade 36. Nozzle 30 iscoupled to wiper support 52 through fasteners such as clips, clamps, orscrews, among other options. In the embodiment shown, nozzles 30 areremovable from wiper support 52 of wiper blade 36 by removing thefastener (clips, clamps, or screws) securing nozzle 30 to wiper support52. In another embodiment, nozzles 30 can be formed integral with wipersupport 52 and wiper blade 36, such that nozzles 30 and wiper blade 36are machined and/or formed from a single-piece construction. Removablenozzles 30 provide the benefit of allowing the nozzles 30 to be removedfrom wiper blade 36 and installed on a new wiper blade 36 duringmaintenance or replacement of wiper blade 36, due to degradation andwear over time. As such, removable nozzles 30 reduce the cost of WWS 10because nozzles 30 can be reused on new or replacement wiper blades 36and nozzles 30 do not need to be purchased for each new or replacementwiper blade 36.

In the embodiments shown in FIGS. 2A-2B, each half of wiper blade 36includes four nozzles 30, or eight total nozzles 30 per wiper blade 36.In another embodiment, wiper blade 36 can include more than or less thaneight nozzles per wiper blade 36. Further, in the embodiment shown, eachone of the plurality of nozzles 30 is spaced equidistance from anadjacent nozzle 30 along a length of wiper blade 36. In anotherembodiment, nozzles 30 can be spaced any distance from an adjacentnozzle 30 such that each nozzle 30 does not need to be spacedequidistance from an adjacent nozzle 30 along a length of wiper blade36. The number of nozzles 30 per wiper blade 36 and the spacing ofnozzles 30 along a length of wiper blade 36 depends on a variety offactors, such as the size of the aircraft, the length of wiper blade 36,and the size of windshield 12, among other factors.

Nozzle 30 includes first side 54, second side 56, input port 58, and atleast one output port 60. First side 54 is a surface of nozzle 30 thatcan be parallel with a portion of wiper support 52 and first side 54faces or points in first sweeping direction 62 of wiper blade 36. Secondside 56 is a surface of nozzle 30 that can be parallel with a portion ofwiper support 52 and second side 56 faces or points in second sweepingdirection 64 of wiper blade 36. First side 54 and second side 56 can beparallel with each other and face in opposite directions. In otherwords, first side 54 faces in a first direction and second side 56 facein a second direction that is approximately 180 degrees from the firstdirection. In the embodiment shown, first side 54 and second side 56 aredescribed as being parallel with each other as well as parallel with aportion of wiper support 52. In another embodiment, first side 54 andsecond side 56 may not be parallel with each other and also may not beparallel with a portion of wiper support 52. Further, in the embodimentshown, first side 54 and second side 56 are shown and described asfacing in opposite directions approximately 180 degrees apart. Inanother embodiment, first side 54 and second side 56 can face indirections that are more or less than 180 degrees apart.

Each nozzle 30 coupled to wiper support 52 of wiper blade 36 includesinput port 58. In the embodiment shown in FIG. 2A, input port 58 of eachnozzle 30 is positioned on a side surface of each nozzle 30, other thanfirst side 54 and second side 56 of nozzle 30. In the embodiment shownin FIG. 2B, input port 58 of each nozzle 30 is positioned on a topsurface of each nozzle 30. In yet another embodiment, input port 58 canbe positioned on any desired surface of nozzle 30. Input port 58 isfluidly coupled to fluid line 28 and input port 58 is configured toreceive fluid from fluid line 28 to be dispensed by nozzle 30. Inputport 58 can be any suitable fluid port that fluidly seals the connectionbetween fluid line 28 and input port 58, preventing leakage between thecomponents. Further, input port 58 can be constructed from a metallic,polymeric, or composite material. In the embodiment shown, a singlefluid line 28 fluidly couples each nozzle 30 in series, such that fluidmust flow through each nozzle 30 along a length of wiper support 52before reaching an end nozzle 30 positioned at an end of wiper support52. In another embodiment, a plurality of fluid lines 28 can extendalong wiper support 52, with each fluid line 28 fluidly coupled to asingle input port 58 (or a multitude of ports) of a single nozzle 30.The fluid lines can be connected to the different nozzles in series orparallel or any combination of both. This configuration allows the fluidto be delivered to certain individual nozzles 30 on the wiper blade 36in order to be applied at certain areas of the windshield 12. This alsoprevents the intermixing of different fluids in the fluid line 28 andallows certain individual nozzles 30 and its corresponding fluid line 28to be designed as per the type of fluid dispersed by them.

Each nozzle 30 coupled to wiper support 52 of wiper blade 36 includes atleast one output port 60 on each of first side 54 and second side 56 ofnozzle 30. In the embodiment shown in FIG. 2A, each nozzle 30 includesone output port 60 positioned on first side 54 and one output port 60positioned on second side 56. In the embodiment shown in FIG. 2B, eachnozzle 30 includes three output ports 60 positioned on first side 54 andthree output ports 60 positioned on second side 56. In yet anotherembodiment, each nozzle 30 can include more than or less than threeoutput ports 60 positioned on each of first side 54 and second side 56of nozzle 30. Output ports 60 positioned on both first side 54 andsecond side 56 allow nozzle 30 to dispense fluid received through inputports 58 from both sides of nozzle 30, in opposite directions. Morespecifically, output ports 60 positioned on first side 54 and secondside 56 allows nozzle 30 to dispense fluid simultaneously in firstsweeping direction 62 and second sweeping direction 64, resulting in amore efficient a thorough cleaning of windshield 12. Output port 60 isfluidly coupled to an interior of nozzle 30 and output port 60 isconfigured to dispense fluid received through input port 58 ontowindshield 12. Output port 60 can be constructed from a metallic,polymeric, or composite material. In the embodiments shown in FIGS.2A-2B, the fluid dispensing from output port 60 of nozzle 30 isconfigured to dispense perpendicular to first side 54 and second side56. In another embodiment, the fluid dispensing from output port 60 candispense at an angle other than perpendicular to first side 54 andsecond side 56.

Further, in the embodiment shown, nozzles 30 are described as dispensingfluid from two sides of nozzle 30. In another embodiment, nozzles 30 caninclude valves within each nozzle 30 that can prevent fluid fromdispensing from first side 54, second side 56, or both sides. The valvescan be connected to controller 22 and a user can interact with userinterface 32 to cause the valves to open or close as desired. In yetanother embodiment, each nozzle 30 can include two fluid lines 28fluidly coupled to two separate input ports 58 of each nozzle 30. Eachinput port 58 can be configured to transfer fluid to either first side54 or second side 56. As such, a user can stop flow to one of the fluidlines, allowing fluid to flow from output port 60 on either first side54 or second side 56. Preventing flow from one side of nozzle 30increases efficiency of WWS 10 because when reaching the sweep limitssome fluid may be dispensed off the windshield onto the aircraft body,which results in waste of fluid and more cost for the airline.

In the embodiment shown, nozzles 30 are described as being stationarywith respect to wiper support 52. In another embodiment, nozzles 30 canbe coupled to wiper support 52 through hinges, such that nozzles 30 canrotate to change the angle of the spray from nozzles 30. Each of thehinges can be connected together through a linkage or each hinge can beindividual and not associated with the other hinges. In an example inwhich a linkage connects each hinge together, an actuating mechanism canbe connected to the hinges and to controller 22, allowing the user tointeract with user interface 32 to change the angle of the hinges andnozzles 30 through commands from controller 22. Further, in an examplein which controller 22 is communicatively coupled to the actuatingmechanism and/or hinges, the hinges can automatically change their angleas wiper 14 sweeps across the windshield of the aircraft. In an examplein which each nozzle is individual, the hinges and nozzles 30 can bemanually adjusted to change the angle of each nozzle 30 along wipersupport 52. The angle of the hinges and nozzles 30 can be changed whilewiper 14 is stationary as well as while wiper 14 sweeps across thewindshield of the aircraft. Changing the angle of nozzles 30 providesthe benefit of increasing efficiency of WWS 10 by allowing each nozzleto target specific areas of the windshield of the aircraft to ensureproper coverage of fluid dispensing from each nozzle 30.

In operation, a user (pilot or co-pilot) can interact with userinterface 32 to activate WWS 10, deactivate WWS 10, control the sweepingspeed of wiper 14, choose the type of fluid (bleed air, water,windshield cleaning fluid, or chemical rain repellant) dispensing fromnozzle 30, control the flow rate of the fluid dispensing from nozzle 30,and control the temperature of the fluid dispensing from nozzle 30. Uponuser interaction with user interface 32, a command signal is transferredfrom user interface 32 to the electrically coupled controller 22indicating an action to be performed by controller 22. Controller 22stores the received command signal within memory 40 and processes thecommand signal using processor(s) 38. Once processed, controller 22sends a command signal to actuator 18 and/or fluid control unit 24. Acommand signal sent to actuator 18 initiates or stops rotation of outputshaft 16, causing wiper 14 to sweep or stop sweeping across windshield12, respectively. Additionally, a command signal can be sent to actuator18 to adjust the rotational speed of output shaft 16 to adjust thesweeping speed of wiper 14 on windshield 12. A command signal sent tofluid control unit 24 can activate or deactivate fluid control unit 24,discussed below.

Activation of fluid control unit 24 can include, but is not limited to,choosing the type of fluid dispensing from nozzle 30, controlling theflow rate of the fluid dispensing from nozzle 30, and controlling thetemperature of the fluid dispensing from nozzle 30. As discussed, theuser can choose the type of fluid (bleed air, water, windshield cleaningfluid, or chemical rain repellant) desired to dispense from nozzle 30 byinteracting with user interface 32. Upon choosing the desired fluid,fluid control unit 24 sends a command signal to begin transferring thefluid from the correct fluid source 26. If bleed air is chosen as thefluid, fluid control unit 24 sends a command signal to bleed air valve48 to open bleed air valve 48 to allow the bleed air from the engine toflow through fluid lines 28 to nozzle 30. If water, windshield cleaningfluid, or chemical rain repellant are chosen as the fluid, fluid controlunit 24 sends a command signal to pump 44 to begin pumping theappropriate fluid from the correct fluid source 26 (water reservoir,windshield cleaning fluid reservoir, or chemical rain repellantreservoir). Simultaneously, fluid control unit 24 sends a command signalto valve 46 indicating that valve 46 should open to allow the fluid toflow through fluid lines 28 to nozzle 30. If the user adjusts the flowrate of the fluid through user interface 32, fluid control unit 24 sendsa command signal to valve 46 to either open or close valve 46 more orless, respectively, to adjust the flow rate of the fluid flowing throughfluid lines 28. Additionally, if the user adjusts the temperature of thefluid through user interface 32, fluid control unit 24 sends a commandsignal to heating element 50 to either increase or decrease thetemperature of heating element 50 to adjust the temperature of the fluidflowing through fluid lines 28 to achieve the desired fluid temperature.

As such, a user can interact with user interface 32 within the cockpitof the aircraft to control many different operations of WWS 10. Incontrast, traditional windshield wiper systems only allow a pilot orco-pilot the options of turning on or turning off the windshield wipersystem and adjusting the speed of the wiper blades. Traditionalwindshield wiper systems do not include the capabilities to choose thefluid type, flow rate, fluid temperature, as well as the sweeping speedof the wipers, as is achieved by WWS 10. Further, traditional windshieldwiper systems include fluid nozzles positioned at the edge of thewindshield of the aircraft, restricting the fluid nozzles to dispensingfluid on only a limited area of the windshield. In contrast, WWS 10includes nozzles 30 coupled to wiper blade 36, such that nozzles 30sweep across windshield 12 with wiper blade 36. This allows nozzles 30to dispense fluid onto a greater area of windshield 12 as wiper blade 36sweeps across windshield 12. Further, the traditional nozzles used onwindshield wiper systems extend through apertures within the body of theaircraft, resulting in additional manufacturing operations and highercost for the airline manufacturers. In contrast, WWS 10 routes fluidlines 28 through the aperture that output shaft 16 extends through,eliminating an extra aperture through the body of the aircraft, whichultimately reduces the cost of the aircraft and WWS 10.

In addition, nozzles 30 of WWS 10 dispense fluid from first side 54 andsecond side 56 of nozzle 30 while sweeping in both first sweepingdirection 62 and second sweeping direction 64. Dispensing fluid fromboth sides of nozzle 30 ensures efficient cleaning of windshield 12 byusing less cleaning fluid than traditional windshield wiper systemsbecause the sweeping nozzles 30 target specific areas on windshield 12to be cleaned instead of spraying over the entire windshield. Further,nozzles 30 sweeping across windshield 12 along with dispensing fluidfrom both sides of nozzles 30 allows fluid to reach a greater area ofwindshield 12, which results in a greater area of windshield 12 beingcleaned. Ultimately, this leads to a safer WWS 10 as compared totraditional windshield wiper systems because the pilot and co-pilot haveincreased view out windshield 12 of the aircraft.

Further, WWS 10 allows a user to activate fluid control unit 24 withoutactivating actuator 18. This provides the benefit of allowing the userto dispense a fluid on windshield 12 without sweeping wiper arm 34across windshield 12. This is advantageous over traditional wipersystems because the user can clear windshield 12 without obstructing theusers view with a sweeping wiper arm 34. For example, a user canactivate fluid control unit 24 to dispense bleed air onto windshield 12to blow dust/sand from windshield 12 or dispense bleed air ontowindshield 12 to melt snow/ice present on windshield 12. In eithercircumstance, sweeping wiper arm 34 across windshield 12 may not benecessary to achieve the desired cleaning effect on windshield 12.Further, clearing windshield 12 without activating actuator 18 resultsin power savings for WWS 10 and the overall aircraft. As described, WWS10 provides many benefits over tradition windshield wiper systems thatwill be appreciated by those skilled in the art. Further, additionalbenefits not specifically described will be realized by those skilled inthe art.

Discussion of Possible Embodiments

The following are non-exclusive descriptions of possible embodiments ofthe present invention.

A windshield wiper system for use on a windshield of an aircraft, thewindshield wiper system comprising: a wiper comprising a wiper arm and awiper blade coupled to a first end of the wiper arm; a nozzle coupled tothe wiper blade, wherein the nozzle is configured to dispense a fluid;an actuator comprising an output shaft, wherein the output shaft iscoupled to a second end of the wiper arm; a controller electricallycoupled to each of the actuator, a user interface, and a fluid controlunit; and a fluid source fluidly coupled to the nozzle through a fluidline.

The windshield wiper system of the preceding paragraph can optionallyinclude, additionally and/or alternatively, any one or more of thefollowing features, configurations and/or additional components:

The actuator is configured to rotate the output shaft to sweep the wiperarm and wiper blade across the windshield of the aircraft.

The controller is configured to: send electrical signals to and receiveelectrical signals from the actuator to control rotation of the outputshaft of the actuator; send electrical signals to and receive electricalsignals from the fluid control unit to control operation of the fluidcontrol unit; and receive electrical signals from the user interfaceindicating an action to be performed by the controller.

The nozzle is removable from the wiper blade.

The fluid dispensing from the nozzle is bleed air, water, windshieldcleaning fluid, or chemical rain repellant.

The bleed air is directed from a gas turbine engine of the aircraft tothe nozzle; the water is directed from a water reservoir to the nozzle;the windshield cleaning fluid is directed from a windshield cleaningfluid reservoir to the nozzle; or the chemical rain repellant isdirected from a chemical rain repellant reservoir to the nozzle.

The fluid control unit includes: a pump configured to force the fluid totravel from the water reservoir, windshield cleaning fluid reservoir, orthe chemical rain repellant reservoir through the fluid line to thenozzle; a bleed air valve configured to allow or prevent bleed air fromflowing through the fluid line to the nozzle; a valve configured tocontrol the flow rate of the fluid travelling from the fluid source andthrough the fluid line; and a heating element configured to increase thetemperature of the fluid travelling through the fluid line before thefluid reaches the nozzle.

The fluid line is routed adjacent the output shaft of the actuator,through a hollow interior of the wiper arm, and to an input port of thenozzle.

The nozzle includes two sides and at least one output port on each ofthe two sides, and wherein the nozzle is configured to dispense fluidfrom the at least one output port on each of the two sides of thenozzle.

Each wiper blade includes a plurality of nozzles coupled to the wiperblade, and wherein each one of the plurality of nozzles is spacedequidistance apart along a length of the wiper blade.

A method of operating a windshield wiper system for use on a windshieldof an aircraft, the method comprising: transferring, by a controller, acommand signal to an electrically coupled fluid control unit to activatethe fluid control unit; transferring, by the fluid control unit, a fluidfrom a fluid source through a fluid line to a nozzle coupled to a wiperblade; and dispensing, by the nozzle, the fluid onto the windshield ofthe aircraft.

The method of the preceding paragraph can optionally include,additionally and/or alternatively, any one or more of the followingfeatures, configurations and/or additional components:

The wiper blade is coupled to a first end of a wiper arm and an actuatorcomprising an output shaft is coupled to a second end of the wiper arm,and wherein the actuator is configured to rotate the output shaft tosweep the wiper arm and the wiper blade across the windshield of theaircraft.

The controller is electrically coupled to the actuator, and wherein thecontroller is configured to send electrical signals to and receiveelectrical signals from the actuator to control rotation of the outputshaft of the actuator.

The fluid line is routed adjacent the output shaft of the actuator,through a hollow interior of the wiper arm, and to an input port of thenozzle.

Receiving, by a user interface, input from a pilot or co-pilot;transferring, by the user interface, a command signal to theelectrically coupled controller indicating an action to be performed bythe controller; and transferring, by the controller, a command signal tothe electrically coupled fluid control unit to activate the fluidcontrol unit.

The fluid dispensing from the nozzle is bleed air, water, windshieldcleaning fluid, or chemical rain repellant.

The bleed air is directed from a gas turbine engine of the aircraft tothe nozzle; the water is directed from a water reservoir to the nozzle;the windshield cleaning fluid is directed from a windshield cleaningfluid reservoir to the nozzle; or the chemical rain repellant isdirected from a chemical rain repellant reservoir to the nozzle.

The step of transferring by the fluid control unit further comprises:pumping, by a pump, the fluid from the water reservoir, the windshieldcleaning fluid reservoir, or the chemical rain repellant reservoirthrough the fluid line to the nozzle; valving, by a bleed air valve, thebleed air to allow or prevent bleed air from flowing through the fluidline to the nozzle; valving, by a valve, the fluid travelling throughthe fluid line to control a flow rate of the fluid in the fluid line;and heating, by a heating element, the fluid travelling through thefluid line to increase the temperature of the fluid before the fluidreaches the nozzle.

The nozzle is removable from the wiper blade; the nozzle includes twosides and at least one output port on each of the two sides; and thenozzle is configured to dispense fluid from the at least one output porton each of the two sides of the nozzle.

Each wiper blade includes a plurality of nozzles coupled to the wiperblade, and wherein each one of the plurality of nozzles is spacedequidistance apart along a length of the wiper blade.

While the invention has been described with reference to an exemplaryembodiment(s), it will be understood by those skilled in the art thatvarious changes may be made and equivalents may be substituted forelements thereof without departing from the scope of the invention. Inaddition, many modifications may be made to adapt a particular situationor material to the teachings of the invention without departing from theessential scope thereof. Therefore, it is intended that the inventionnot be limited to the particular embodiment(s) disclosed, but that theinvention will include all embodiments falling within the scope of theappended claims.

The invention claimed is:
 1. A method of operating a windshield wipersystem for use on a windshield of an aircraft, the method comprising:transferring, by a controller, a command signal to an electricallycoupled fluid control unit to activate the fluid control unit;transferring, by the fluid control unit, a fluid from one of a pluralityof fluid sources through a fluid line to a nozzle coupled to a wiperblade; and dispensing, by the nozzle, the fluid onto the windshield ofthe aircraft; wherein the wiper blade is coupled to a first end of awiper arm and an actuator comprising an output shaft is coupled to asecond end of the wiper arm, and wherein the actuator is configured torotate the output shaft to sweep the wiper arm and the wiper bladeacross the windshield of the aircraft; wherein the controller iselectrically coupled to the actuator, the fluid control unit, and a userinterface, and wherein the controller is configured to: send electricalsignals to and receive electrical signals from the actuator to controlrotation of the output shaft of the actuator send electrical signals toand receive electrical signals from the fluid control unit to controldispensing of fluid through the nozzle; and send receive command signalsfrom the user interface indicating an action to be performed by thecontroller; wherein each of the plurality of fluid sources is configuredto dispense a different fluid through the nozzle and the user interfaceis configured to permit a user to choose which of the different fluidsis dispensed through the nozzle.
 2. The method of claim 1, wherein thefluid line is routed adjacent the output shaft of the actuator, througha hollow interior of the wiper arm, and to an input port of the nozzle.3. The method of claim 1 and further comprising: receiving, by the userinterface, input from a pilot or co-pilot; transferring, by the userinterface, a command signal to the electrically coupled controllerindicating an action to be performed by the controller; andtransferring, by the controller, a command signal to the electricallycoupled fluid control unit to activate the fluid control unit.
 4. Themethod of claim 1, wherein the fluid dispensing from the nozzle can beselected from two or more of bleed air, water, windshield cleaningfluid, or chemical rain repellant.
 5. The method of claim 4, wherein:the bleed air is directed from a gas turbine engine of the aircraft tothe nozzle; the water is directed from a water reservoir to the nozzle;the windshield cleaning fluid is directed from a windshield cleaningfluid reservoir to the nozzle; or the chemical rain repellant isdirected from a chemical rain repellant reservoir to the nozzle.
 6. Themethod of claim 5, wherein the step of transferring by the fluid controlunit further comprises: pumping, by a pump, the fluid from the waterreservoir, the windshield cleaning fluid reservoir, or the chemical rainrepellant reservoir through the fluid line to the nozzle; valving, by ableed air valve, the bleed air to allow or prevent bleed air fromflowing through the fluid line to the nozzle; valving, by a valve, thefluid travelling through the fluid line to control a flow rate of thefluid in the fluid line; and heating, by a heating element, the fluidtravelling through the fluid line to increase a temperature of the fluidbefore the fluid reaches the nozzle.
 7. The method of claim 1, wherein:the nozzle is removable from the wiper blade; the nozzle includes twosides and at least one output port on each of the two sides; and thenozzle is configured to dispense fluid from the at least one output porton each of the two sides of the nozzle.
 8. The method of claim 1,wherein each wiper blade includes a plurality of nozzles coupled to thewiper blade, and wherein each one of the plurality of nozzles is spacedequidistance apart along a length of the wiper blade.
 9. The windshieldwiper system of claim 1, wherein each wiper blade includes a pluralityof nozzles coupled to the wiper blade, and wherein each one of theplurality of nozzles is spaced equidistance apart along a length of thewiper blade.
 10. A method of operating a windshield wiper system for useon a windshield of an aircraft, the method comprising: transferring, bya controller, a command signal to an electrically coupled fluid controlunit to activate the fluid control unit; transferring, by the fluidcontrol unit, a fluid from a fluid source through a fluid line to anozzle coupled to a wiper blade; dispensing, by the nozzle, the fluidonto the windshield of the aircraft; receiving, by a user interface,input from a pilot or co-pilot; transferring, by the user interface, acommand signal to the electrically coupled controller indicating anaction to be performed by the controller; and transferring, by thecontroller, a command signal to the electrically coupled fluid controlunit to activate the fluid control unit; wherein the wiper blade iscoupled to a first end of a wiper arm and an actuator comprising anoutput shaft is coupled to a second end of the wiper arm, and whereinthe actuator is configured to rotate the output shaft to sweep the wiperarm and the wiper blade across the windshield of the aircraft; whereinthe fluid dispensing from the nozzle is bleed air, water, windshieldcleaning fluid, or chemical rain repellant; wherein: the nozzle isremovable from the wiper blade; the nozzle includes two sides and atleast one output port on each of the two sides; and the nozzle isconfigured to dispense fluid from the at least one output port on eachof the two sides of the nozzle; and wherein each wiper blade includes aplurality of nozzles coupled to the wiper blade, and wherein each one ofthe plurality of nozzles is spaced equidistance apart along a length ofthe wiper blade.
 11. The method of claim 10, wherein the controller iselectrically coupled to the actuator, and wherein the controller isconfigured to send electrical signals to and receive electrical signalsfrom the actuator to control rotation of the output shaft of theactuator.
 12. The method of claim 10, wherein the fluid line is routedadjacent the output shaft of the actuator, through a hollow interior ofthe wiper arm, and to an input port of the nozzle.
 13. The method ofclaim 10, wherein: the bleed air is directed from a gas turbine engineof the aircraft to the nozzle; the water is directed from a waterreservoir to the nozzle; the windshield cleaning fluid is directed froma windshield cleaning fluid reservoir to the nozzle; or the chemicalrain repellant is directed from a chemical rain repellant reservoir tothe nozzle.
 14. The method of claim 13, wherein the step of transferringby the fluid control unit further comprises: pumping, by a pump, thefluid from the water reservoir, the windshield cleaning fluid reservoir,or the chemical rain repellant reservoir through the fluid line to thenozzle; valving, by a bleed air valve, the bleed air to allow or preventbleed air from flowing through the fluid line to the nozzle; valving, bya valve, the fluid travelling through the fluid line to control a flowrate of the fluid in the fluid line; and heating, by a heating element,the fluid travelling through the fluid line to increase a temperature ofthe fluid before the fluid reaches the nozzle.
 15. A windshield wipersystem for use on a windshield of an aircraft, the windshield wipersystem comprising: a wiper comprising a wiper arm and a wiper bladecoupled to a first end of the wiper arm; a nozzle coupled to the wiperblade, wherein the nozzle is configured to dispense a fluid; an actuatorcomprising an output shaft, wherein the output shaft is coupled to asecond end of the wiper arm and the actuator is configured to rotate theoutput shaft to sweep the wiper arm and wiper blade across thewindshield of the aircraft; a controller electrically coupled to each ofthe actuator, a user interface, and a fluid control unit wherein thecontroller is configured to: send electrical signals to and receiveelectrical signals from the actuator to control rotation of the outputshaft of the actuator; send electrical signals to and receive electricalsignals from the fluid control unit to control operation of the fluidcontrol unit; and receive electrical signals from the user interfaceindicating an action to be performed by the controller; and a pluralityof fluid sources fluidly coupled to the nozzle through a fluid line,wherein each of the plurality of fluid sources is configured to dispensea different fluid through the nozzle, wherein the fluid dispensing fromthe nozzle can be selected from two or more of bleed air, water,windshield cleaning fluid, or chemical rain repellant, and wherein theuser interface is configured to permit a user to choose which of thedifferent fluids is dispensed through the nozzle.
 16. The windshieldwiper system of claim 15, wherein the nozzle is removable from the wiperblade.
 17. The windshield wiper system of claim 15, wherein: the bleedair is configured to be directed from a gas turbine engine of theaircraft to the nozzle; the water is directed from a water reservoir tothe nozzle; the windshield cleaning fluid is directed from a windshieldcleaning fluid reservoir to the nozzle; or the chemical rain repellantis directed from a chemical rain repellant reservoir to the nozzle. 18.The windshield wiper system of claim 17, wherein the fluid control unitincludes: a pump configured to force the fluid to travel from the waterreservoir, windshield cleaning fluid reservoir, or the chemical rainrepellant reservoir through the fluid line to the nozzle; a bleed airvalve configured to allow or prevent bleed air from flowing through thefluid line to the nozzle; a valve configured to control a flow rate ofthe fluid travelling from the fluid source and through the fluid line;and a heating element configured to increase a temperature of the fluidtravelling through the fluid line before the fluid reaches the nozzle.19. The windshield wiper system of claim 15, wherein the fluid line isrouted adjacent the output shaft of the actuator, through a hollowinterior of the wiper arm, and to an input port of the nozzle.
 20. Thewindshield wiper system of claim 15, wherein the nozzle includes twosides and at least one output port on each of the two sides, and whereinthe nozzle is configured to dispense fluid from the at least one outputport on each of the two sides of the nozzle.